XFOIL Version 6.96 Calculated polar for: DEFIANT CANARD BL145 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4106 0.09541 0.09040 -0.0230 1.0000 0.1152 -8.500 -0.4393 0.09214 0.08728 -0.0285 1.0000 0.1197 -8.250 -0.4900 0.08840 0.08360 -0.0351 1.0000 0.1205 -8.000 -0.4319 0.08479 0.08004 -0.0267 1.0000 0.1245 -7.750 -0.4279 0.08216 0.07746 -0.0256 1.0000 0.1282 -7.500 -0.4445 0.07889 0.07430 -0.0268 1.0000 0.1322 -7.250 -0.4926 0.07346 0.06877 -0.0334 1.0000 0.1377 -7.000 -0.4665 0.07076 0.06625 -0.0295 1.0000 0.1407 -6.750 -0.4607 0.06822 0.06375 -0.0279 1.0000 0.1455 -6.500 -0.4822 0.06396 0.05934 -0.0300 1.0000 0.1554 -6.250 -0.4678 0.06147 0.05699 -0.0272 1.0000 0.1594 -6.000 -0.4768 0.05827 0.05362 -0.0273 1.0000 0.1726 -5.750 -0.4640 0.05583 0.05132 -0.0247 1.0000 0.1772 -5.500 -0.4645 0.05315 0.04855 -0.0236 1.0000 0.1914 -5.250 -0.4563 0.03733 0.03035 -0.0246 1.0000 0.0692 -5.000 -0.4410 0.03468 0.02759 -0.0228 1.0000 0.0645 -4.750 -0.4259 0.03164 0.02372 -0.0200 1.0000 0.0578 -4.500 -0.4095 0.02949 0.02140 -0.0183 1.0000 0.0566 -4.250 -0.3923 0.02770 0.01936 -0.0166 1.0000 0.0555 -4.000 -0.3746 0.02634 0.01775 -0.0149 1.0000 0.0559 -3.750 -0.3565 0.02523 0.01643 -0.0133 1.0000 0.0567 -3.500 -0.3388 0.02443 0.01538 -0.0117 1.0000 0.0581 -3.250 -0.2912 0.02278 0.01372 -0.0155 0.9916 0.0604 -3.000 -0.2424 0.02156 0.01255 -0.0193 0.9819 0.0644 -2.750 -0.1967 0.02034 0.01140 -0.0226 0.9701 0.0711 -2.500 -0.1517 0.01914 0.01037 -0.0258 0.9581 0.0946 -2.250 -0.1281 0.01574 0.00965 -0.0251 0.9468 0.5965 -2.000 -0.0965 0.01521 0.00993 -0.0228 0.9344 0.8134 -1.750 -0.0359 0.01526 0.00999 -0.0266 0.9249 0.9085 -1.500 0.0681 0.01547 0.00989 -0.0391 0.9228 0.9629 -1.250 0.1803 0.01510 0.00922 -0.0542 0.9196 0.9913 -1.000 0.2498 0.01443 0.00835 -0.0625 0.9013 1.0000 -0.750 0.2966 0.01390 0.00762 -0.0662 0.8747 1.0000 -0.500 0.3360 0.01354 0.00706 -0.0684 0.8460 1.0000 -0.250 0.3671 0.01336 0.00667 -0.0690 0.8178 1.0000 0.000 0.3907 0.01334 0.00646 -0.0682 0.7911 1.0000 0.250 0.4124 0.01339 0.00633 -0.0669 0.7666 1.0000 0.500 0.4340 0.01350 0.00625 -0.0656 0.7443 1.0000 0.750 0.4552 0.01365 0.00622 -0.0641 0.7235 1.0000 1.000 0.4753 0.01384 0.00627 -0.0625 0.7028 1.0000 1.250 0.4960 0.01404 0.00633 -0.0609 0.6828 1.0000 1.500 0.5169 0.01425 0.00641 -0.0593 0.6630 1.0000 1.750 0.5381 0.01448 0.00651 -0.0578 0.6436 1.0000 2.000 0.5595 0.01471 0.00663 -0.0563 0.6243 1.0000 2.250 0.5811 0.01497 0.00677 -0.0548 0.6053 1.0000 2.500 0.6027 0.01523 0.00692 -0.0533 0.5861 1.0000 2.750 0.6243 0.01550 0.00708 -0.0518 0.5664 1.0000 3.000 0.6459 0.01579 0.00725 -0.0503 0.5463 1.0000 3.250 0.6678 0.01610 0.00743 -0.0489 0.5262 1.0000 3.500 0.6897 0.01646 0.00765 -0.0475 0.5066 1.0000 3.750 0.7115 0.01685 0.00794 -0.0461 0.4870 1.0000 4.000 0.7331 0.01726 0.00826 -0.0447 0.4680 1.0000 4.250 0.7557 0.01770 0.00859 -0.0435 0.4514 1.0000 4.500 0.7782 0.01816 0.00899 -0.0424 0.4362 1.0000 4.750 0.8003 0.01864 0.00949 -0.0413 0.4219 1.0000 5.000 0.8229 0.01914 0.00997 -0.0402 0.4092 1.0000 5.250 0.8462 0.01959 0.01033 -0.0392 0.3971 1.0000 5.500 0.8686 0.01993 0.01058 -0.0381 0.3836 1.0000 5.750 0.8891 0.02026 0.01096 -0.0367 0.3694 1.0000 6.000 0.9106 0.02066 0.01139 -0.0355 0.3570 1.0000 6.250 0.9339 0.02112 0.01176 -0.0346 0.3464 1.0000 6.500 0.9553 0.02153 0.01225 -0.0334 0.3349 1.0000 6.750 0.9764 0.02201 0.01279 -0.0322 0.3236 1.0000 7.000 0.9988 0.02246 0.01318 -0.0311 0.3125 1.0000 7.250 1.0194 0.02285 0.01360 -0.0299 0.3000 1.0000 7.500 1.0385 0.02331 0.01415 -0.0283 0.2868 1.0000 7.750 1.0573 0.02377 0.01464 -0.0268 0.2724 1.0000 8.000 1.0752 0.02428 0.01517 -0.0251 0.2567 1.0000 8.250 1.0918 0.02489 0.01575 -0.0233 0.2393 1.0000 8.500 1.1072 0.02564 0.01645 -0.0214 0.2205 1.0000 8.750 1.1217 0.02649 0.01726 -0.0194 0.2022 1.0000 9.000 1.1355 0.02729 0.01805 -0.0173 0.1862 1.0000 9.250 1.1495 0.02811 0.01891 -0.0152 0.1729 1.0000 9.500 1.1639 0.02905 0.01990 -0.0133 0.1617 1.0000 9.750 1.1794 0.03003 0.02087 -0.0116 0.1528 1.0000 10.000 1.1951 0.03104 0.02187 -0.0100 0.1450 1.0000 10.250 1.2110 0.03241 0.02334 -0.0085 0.1386 1.0000 10.500 1.2274 0.03362 0.02457 -0.0072 0.1328 1.0000 10.750 1.2452 0.03518 0.02614 -0.0062 0.1279 1.0000 11.000 1.2568 0.03669 0.02788 -0.0043 0.1234 1.0000 11.250 1.2755 0.03816 0.02933 -0.0034 0.1196 1.0000 11.500 1.2956 0.04028 0.03149 -0.0030 0.1165 1.0000 11.750 1.3007 0.04235 0.03391 -0.0006 0.1143 1.0000 12.000 1.3061 0.04445 0.03628 0.0016 0.1121 1.0000 12.250 1.3104 0.04645 0.03848 0.0038 0.1099 1.0000 12.500 1.3180 0.04842 0.04056 0.0055 0.1078 1.0000 12.750 1.3417 0.05125 0.04336 0.0049 0.1054 1.0000 13.000 1.3276 0.05392 0.04634 0.0086 0.1048 1.0000 13.250 1.3091 0.05689 0.04962 0.0119 0.1044 1.0000 13.500 1.2864 0.06043 0.05346 0.0143 0.1042 1.0000 13.750 1.2597 0.06474 0.05805 0.0154 0.1041 1.0000 14.000 1.2268 0.07016 0.06373 0.0151 0.1042 1.0000 14.250 1.1886 0.07706 0.07086 0.0129 0.1045 1.0000 14.500 1.1436 0.08608 0.08007 0.0087 0.1050 1.0000